Aeroballistic diagnostic system

Abstract

A system which is packaged within a projectile fuze body and obtains data relative to the projectile during a launch. Sensors are provided which obtain in-bore data as well as in-flight data. The in-bore data is recorded at a fast rate during in-bore travel of the projectile and is read out, continuously, at a slower rate during in-flight travel. Both in-bore data and in-flight data are encoded and transmitted to a ground station for analysis.

What is claimed is:  
     
       1. An aeroballistic diagnostic system for obtaining information relative to flight of a projectile launched from the bore of a gun, comprising: 
       a container adapted to be attached to said projectile;  
       a plurality of sensor arrays positioned within said container;  
       at least one of said arrays being operable to obtain projectile data during in-bore travel of said projectile;  
       remaining ones of said arrays being operable to obtain projectile data during in-flight travel of said projectile;  
       recording means carried by said container and operable to sample and store said in-bore data and to output said stored data after said projectile exits said gun;  
       utilization means for receiving encoded data; and  
       encoding means operable to encode said in-bore data which is output from said recording means, as well as to encode said data provided by said remaining ones of said arrays, and to provide the encoded data to said utilization means.  
     
     
       2. A system according to  claim 1  wherein: 
       said container is aerodynamically shaped and is positionable on the front end of said projectile.  
     
     
       3. A system according to  claim 2  wherein: 
       said container is a fuze body having an interior into which said sensor arrays, said recording means and said encoding means are packaged.  
     
     
       4. A system according to  claim 3  which includes: 
       a potting material within said interior.  
     
     
       5. A system according to  claim 3  wherein: 
       said utilization means includes a transmitter and transmitter antenna for transmitting said data to a remote location.  
     
     
       6. A system according to  claim 5  wherein: 
       said transmitter and transmitter antenna are also packaged within said interior of said fuze body.  
     
     
       7. A system according to  claim 3  wherein: 
       said fuze body has a threaded portion which threads into the front of said projectile and replaces the conventional fuze of said projectile.  
     
     
       8. A system according to  claim 3  wherein: 
       said recording means records at a first rate and outputs, repetitively, at a second rate which is slower than said first rate.  
     
     
       9. A system according to  claim 8  wherein: 
       said output rate is {fraction (1/10)} said input rate.  
     
     
       10. A system according to  claim 1  which includes: 
       a normally open g-switch;  
       said g-switch being operable to start said recording means when said g-switch closes, due to a predetermined acceleration.  
     
     
       11. A system according to  claim 1  wherein: 
       one of said arrays obtains data relative to in-bore axial acceleration of said projectile; and  
       another of said arrays obtains data relative to in-flight axial acceleration of said projectile.  
     
     
       12. A system according to  claim 11  wherein: 
       said projectile additionally rotates during launch and in-flight; and wherein  
       another of said arrays obtains data relative to in-bore radial acceleration of said projectile; and  
       yet another of said arrays obtains data relative to in-flight radial acceleration of said projectile.  
     
     
       13. A system according to  claim 11  wherein: 
       said projectile includes a plurality of moveable control surfaces for controlling directional flight of said projectile;  
       said utilization means includes an in-flight guidance control circuit for governing operation of said control surfaces; and wherein  
       said utilization means additionally includes a microprocessor responsive to data provided by said encoding means to regulate said in-flight guidance control circuit.  
     
     
       14. A system according to  claim 11  wherein: 
       said projectile carries a main explosive charge; and which includes  
       a detonator positioned within said container at a location to cause ignition of said main explosive charge under predetermined conditions.  
     
     
       15. A system according to  claim 6  wherein: 
       said fuze body includes a nose portion;  
       said transmitter and transmitter antenna being packaged within said nose portion.  
     
     
       16. A system according to  claim 15  wherein: 
       said nose portion is of a non-metallic material.  
     
     
       17. A system according to  claim 16  wherein: 
       said nose portion includes a nose tip;  
       said nose tip being of a ceramic material.